Pedal construction



Jul 21, 1936. A. H. HOFER PEDAL CONSTRUCTION Filed June 28', 1933 2Sheets-Sheet 1 fig Z July 21, 1936.

A. H. HOFER PEDAL CONSTRUCTION Filed June 28, 1953 2 Sheets-Sheet 2INVENTOR. ALF/2E0 H. Harm BY W 2?. 5o?

ATTORNEY atente J y 9 W3 PEDAL CONSTRUCTION Alfred H. Hofer, Dayton,Qhio, assignor to Bendix Aviation Corporation, South Bend, End, acorporation of Delaware Application June 2 8, 1933, Serial No. 677,969

13 Claims.

This invention relates to aircraft controls and particularly to brakeand rudder controls.

One of the objects of this invention is to provide in combination simpleand efficient means for controlling the rudder and associated simple andefl'icient means for controlling the wheel brakes independently of eachother and of the rudder.

A further object is to provide means for po- 11c brakes are released.

A further object is to provide simple and convenient means for adjustingthe rudder cables A further feature is a slide and locking device bywhich the rudder pedal is connected to the rudder cables.

Further objects and features of the invention will be apparent after areading of the subjoined specification and claims and afterconsideration of the accompanying drawings, in which:

Figure 1 is a view in side elevation of an aircontrol, a portion of thecovering having been removed to show one of the pedals;-

Figure 2 is a view in rear elevation showing the rudder and brake pedalson an enlarged scale and mostly in elevation but having parts shown insection;

. Figure 3 is a side view in vertical section taken substantially on theline 3--3 of Figure 2;

Figure 4 is a fragmentary view in vertical sec- Referring to Figure 1 ofthe drawings, there is shown an airplane"! having a rudder l2 andlanding wheels such as l4. Each wheel is equipped with a brake l8. 55 r'The rudder is controlled by rudder pedals sitioning the brake controlelements when the plane equipped with my novel brake and rudder tiontaken substantially on the line 4-4 of Fig- (Cl. Zed-Ell) through ruddercontrol cables such as it and the brake is controlled by brake pedalsassociated with the rudder pedals through brake con trol cables such as20. p

The combined brake and rudder pedals are 5 shown most clearly in Figures2 and 3. Secured to the frame of the airplane is a shaft 22. On this aremounted a pair of frames 24 and 26 which serve as rudder controlpedals.- Each frame comprises a pair of sleeves 28 and 30, a pair oftubular side elements 32 and 34 each secured to one of the sleeves andan upper tubular element 36 joining the side elements. Pins 38 securedin the shaft maintain the frames or pedals in the desired position.

As shown in Figures 2 and 4 each rudder pedal is connected to the ruddercontrol cable by a novel slide and releasable lock arrangement. Securedat the junction between the side element 32 and the upper element 36 area pair of plates 40 and E2, the plates being formed with aligned holes.Secured to the outer plate 42 is a tube 44 carrying at its outer end aplug 46. Extending through the plug 56 and the tube 44 is a bolt d8having a shoulder 50 adapted normally to bear against the plate 32.Positioned between the shoulder 50 and the plug 56 is a spring 52 whichurges the bolt inward. Secured to the bolt outside of the plug is a sideplate 54 by means of which the pilot by a side thrust of his foot isable to move the pin outward compressing the spring.

The rudder cable I8 is connected to' an arcual plate 56 formed with aseries of holes such as 58 and 60. This plate extends through the spacebetween the plates and 42 and the holes 58, 6.0, etc. are adapted toalign with the aligned holes in the plates 40 and 42. Thus the bolt 48is normally maintained to extend through one of the holes in the arcualplate 56 and through a pair of aligned holes in the plates 40 and 4.2and thus the cable I8 is adjustably secured to the ruddercontrol pedai.The forward end of the arcual plate is connected to a cable 62 which isconnected at its forward end with a spring 64. By means of thisarrangement the pilot may adjust the rudder control cables to positionthe pedals most comfortably for him, taking into consideration thelength of his legs and changes of position which he may desire from timeto time.

Referring again to Figures 2 and 3, it may be seen that each rudderpedal has a brake operating pedal mounted thereon. Thus the uppertubular element of the rudder pedal 24 has the brake pedal 66 sleevedthereon and the corrc- 6s spending element of the rudder pedal 26 hasthe brake pedal 68 sleeved thereon. The brake ped als 66 and 68 are thusmounted for rotation on the rudder pedals. Each comprises a curved 5foot pad I and a T-shaped bracing member 12 riveted thereto.

Angular movement of the brake pedals 66 and 68 is transmitted to thebrake control cables by a parallelogram arrangement. Thus that 10 thereis no distortion due to the position of the rudder pedal. Sleeves I4 andI6 mounted on the shaft 22 each have secured thereto arms such as I8.each of these arms I8 are links 80 which extend 15 upward and are alsopivotally connected at their upper ends to the associated bracing memberI2. The distance between the centers of the pivotal connections at theends of the links 60 equals the distance between the centers of the 20shaft 22 and the tubular element 36. The dis tance between the center oftheshaft 22 and the center of the pivotal connection at the lower end ofeach link 80 equals the distance between the center of each tubularelement 36 and the center of the pivotal connection at the upper 'end ofeach link 80. Secured to the sleeves I4 and I6 are curved tubular arms82 and 84 to the lower ends of each of which are secured one of thecables 20.

30 Secured to the lateral center of the shaft 22 is a tubular T-shapedstop member 86. The outer cross elements of this member is normallycontacted by the levers 82 and 84 so that the brake operating pedals 66and 68 are maintained 5 in a predetermined definite position regardlessof the position of the rudder pedals, the arms 82 and 84 being held incontact by the release springs at the brakes I6.

In the modification shown in Figure 5 the latch 40 comprising the pin 48is replaced by somewhat similar structure. The tubular side element I32is formed with a slot I33 through which extends an arcual plate I56formed with holes similar to the holes 58 and 60. A bolt I48 ex- 45tends into a bore in the element I32 transverse to the slot and throughone of the holes in the plate I56. A pin I56 extends transverselythrough the bolt I48 and eccentrically through a cam I53. The cam I53limits the inward 5o movement of the bolt I48 and a spring I52 bearsagainst the pin I50 to urge the bolt inward. The cam I53 is providedwith a lever I54 by means of which it may be rotated to withdraw thebolt from the holes in the plate I56 and allow ad- 55 justment of thepedal.

Another modification of the latch mechanism is shown in Figure 6.Therein the upper tubular element 236 is provided with annular plugs 242and 246. The bolt 248 is considerably longer 0 and extends through themember 236 and the plug 246. An extension 249 screwed onto the end ofthe bolt 248 extends through the plug 242. Secured to side element 234is a bracket 240 formed with a hole into which the exten- 65 -sion 249normally projects. The bolt 248 is provided with an abutment 256 and aspring 252 is positioned between the abutment 250 and the plug 246. Ashoulder 25I is provided on the extension 249, and positioned betweenthe shoulder 70 25I and the bracket 246 is an arcual plate 256 which issecured at its rear end to one of the rudder control cables. Pivoted ona lug 233 on side element 232 is a lever 254 which is pivotallyconnected to the inner end of the bolt 248.

7 Thereby the pilot may by a side movement of Pivotally connected to theouter ends of his foot withdraw the bolt from its locking hole.

It is believed that the operation of all three embodiments is obviousfrom the above description. Movement of the pedals 24 and 26 act throughcables I8 to operate the rudder I2. Dur- 5 ing normal flying the brakerelease'spring will maintain the arms 82 and 84 in contact with the stop86 and thus maintain the pedals 66 and 68 in predetermined position. Thepilot may by his toes depress the pedals 66 and 68 and thus move thearms 82 and '84 away from the stop 86. This movement exerts tension onthe cables 26 and applies the brakes. Inasmuch as the pedals 66 and 68are entirely independent the brakes may be operated concurrently withequal pressures or with any desired proportion of pressures or eitherone may be operated separately. Because of the parallelogram hookup,movement of the rudder pedals does not aiiect the brake control andequal movement of the brake pedal effects equal brake energizationregardless of position of the rudder pedals.

The pilot may at any time adjust the position of the pedals relative tothe cables by moving the latch lever or plate (54, I54 or 254) outwardto release the connection with the cable, moving the pedal to thedesired position, and releasing the latch.

It is to be understood that the above described embodiments of myinvention are for the pur- 80 pose of illustration only and variouschanges may be made therein without departing from the spirit and scopeof the invention.

I claim:

1. In airplane control apparatus a rudder pedal, a brake pedal pivotallymounted thereon,

a lever pivoted on the axis of the rudder pedal, and a link pivotallyconnecting the lever and the brake pedal having a length between pivotsequal to the distance between the axes of the rudder pedal and brakepedal. v

2. In airplane control apparatus a rudder,

a rudder pedal for controlling said rudder, a brake, a brake pedal forcontrolling said brake mounted on a movable part of said rudder pedal,means for connecting said brake pedal to said brake includingconnections immovable during rudder operating movements of the rudderpedal except when the angle 01 the brake pedal is changed. e

3; In airplane controls, a rudder, a rudder pedal. a connecting cablefor the rudder, a plate formed with a series of holes connected to thecable, and means comprising a resiliently pressed bolt adapted to fit inany of said holes for selectively latching the rudder pedal to themember.

4. In airplane controls, a rudder, a rudder pedal, a connecting cablefor the rudder, a member connected to the cable, means for selectively80 latching the rudder pedal to the member, and a member associated withthe latching means and mounted on the rudder pedal and movabletransversely by the pilot's foot for'releasing the latching means. 85

5. In airplane controls, a rudder, a rudder pedal, 2. connecting cablefor the rudder, a member connected to the cable, and means forselectively latching the ruuder pedal to the member, said latching meansincluding a tube mounted 70 on the rudder pedal, and a spring pressedplunger within said tube.

6. In airplane controls, a rudder, a rudder pedal, a connecting cablefor the rudder, a member connected to the cable, and means forselectively latching the rudder pedal to the member, said pedalincluding a tubular side element formed with a slot and with a boretransversely of the slot, and said latching means including incombination with said side element a bolt in said bore, a spring actingon said bolt, a pin through said bolt, a cam rotatably mounted on saidpin,

and means to rotate said cam.

7. In airplane controls, a rudder, a rudder pedal, a connecting cablefor the rudder, a member connected to the cable, means for selectivelylatching the rudder pedal to the member, said' rudder pedal including aside tubular element, an upper tubular element, and said latching meansincluding in combination with said upper tubular element a springpressed bolt extending through said upper element, and a lever pivotallymounted on said side element and connected to said bolt.

8. Airplane control apparatus comprising a shaft, a series of sleevesmounted on said shaft, rudder control pedals mounted on, some of saidsleeves, and brake control mechanisms mounted on others of said sleeves.

9. Airplane control apparatus comprising a shaft, a series of sleevesmounted on said shaft, rudder control pedals mounted on some of saidsleeves, brake control mechanisms each provided with an arm and eachmounted on one of the others of said sleeves, brake control pedalsrotatably mounted on said rudder control pedals, and an inextensiblelink by which each arm isconnected to the associated brake controlpedal.

l0. Airplane control apparatus comprising a shaft, a series of sleevesmounted on said shaft, rudder control pedals mounted on some of saidsleeves, brake control mechanisms each carrying an arm and each mountedon one of the others of said sleeves, brake control pedals rotatablymounted on said rudder control pedals, and an inextensible linkpivotally connected to the brakecontrol pedal and the arm.

11. Airplane control apparatus comprising a shaft, a series of sleevesmounted on said shaft, rudder control pedals mounted on some of saidsleeves, brake control mechanisms each having an arm and each mounted onone of the others of said sleeves, and a stop secured to said shaft withwhich said arms contact when the brakes are released.

12. Airplane control apparatus comprising a shaft, a brake, a ruddercontrol pedal rotatably mounted on said shaft, a brake operatingmechanism rotatably mounted on said shaft, and a stop member secured tosaid shaft with which a portion of said mechanism contacts when thebrake is released.

13. Airplane control apparatus comprising a shaft, brakes, ruddercontrol pedals rotatably mounted on said shaft, brake operatingmechanisms rotatably mounted on said shaft, and a T-shaped stop membersecured to said shaft with which a portion of each of said brakeoperating 30 mechanisms contacts when the brakes are released.

ALFRED H. HOFER.

